Methodology and Results of Optimizing the Ascent Stage in the Problem of Vertical Navigation of Civil and Military Transport Aircraft

The problem of forming the altitude-speed profile of the flight of civil and military transport aircraft (AC) at the ascent stage and optimization according to the economic criterion is solved using a dynamic model of the motion of the center of mass in a vertical plane. The model takes into account the change in the mass of the AC and the systematic component of the wind speed. The aerodynamic characteristics of the AC and its weight, as well as the altitude and speed characteristics and the throttle characteristics of the engines, are close to those of a modern typical medium-range AC. For the given ascent scenario, the optimal and quasi-optimal control laws are found at the acceleration stage. The influence of the scenario’s parameters on the values of the main optimization criteria is estimated. The dependences of the optimal values of the ascent rate on the cost index are obtained and the range of its variability is found.